Method for piloting an aircraft in approach phase
View Patent ↗According to the invention, high lift leading-edge slats ( 13 ) and high lift flaps ( 14 ) are simultaneously deployed, when the speed of the aircraft is equal to and less than an AES threshold.
1. A method for piloting an aircraft for approach to final descent, said aircraft being provided with wings having leading-edge high-lift slats and trailing-edge high-lift flaps, said slats and flaps being controllable by a control lever, wherein said method comprises the steps of:
maintaining said slats and said flaps in a retracted position prior to the approach to the final descent;
adjusting the aircraft to a first configuration as said aircraft begins said approach to the final descent and aircraft speed falls below a first predetermined speed value, wherein the first configuration is produced by both extending and inclining said slats from the retracted position, while maintaining the flaps in the retracted position;
adjusting the aircraft to a second configuration as said aircraft follows said approach to the final descent and aircraft speed falls below a second predetermined speed value that is less than said first speed value, wherein the second configuration is produced by both extending and inclining said flaps relative to the position of the flaps in the first configuration, while maintaining said slats substantially as in the position of the slats in said first configuration; and
conferring on said wings, while said control lever is in a position corresponding to said first configuration and said aircraft crosses a first speed threshold greater than said second predetermined speed value, an intermediate configuration, wherein the intermediate configuration is produced by maintaining said slats in an extended and inclined position substantially as in said first and second configurations, and extending the flaps less than in said second configuration and greater than in said first configuration; and
retracting the flaps to a configuration substantially as that of the first configuration while said wings are in said intermediate configuration and aircraft speed crosses a second speed threshold greater than said first speed threshold.
2. The method as claimed in claim 1 , wherein said first speed threshold is substantially equal to said first predetermined speed value.
3. The method as claimed in claim 1 , wherein said first speed threshold is greater than said first predetermined speed value.
4. The method as claimed in claim 1 , wherein said second speed threshold is greater than said first speed threshold.
5. The method as claimed in claim 1 , wherein, in said intermediate configuration, said flaps are extended, but not inclined.
6. The method as claimed in claim 1 , wherein, in said intermediate configuration, said flaps are extended and inclined.
7. The method as claimed in claim 6 , wherein, in said intermediate configuration, said flaps are less inclined than in said second configuration.
8. The method as claimed in claim 6 , wherein said intermediate configuration corresponds to a take-off configuration of the aircraft.
9. An aircraft, controlled according to the method of claim 1 .
10. The method as in claim 1 , wherein the first speed threshold is both greater than said second predetermined speed value and substantially equal to or greater than said first speed value.